Method of launching a spacecraft into low earth orbit using a non-line-of-sight optical power transfer system

Abstract

A method of launching a spacecraft into low Earth orbit using a non-line-of-sight optical power transfer system. The method includes generating optical power at a base station and using an optical fiber to transmit the optical power generated to a launch vehicle via an actively cooled fiber spooler thereon. The optical power received by the launch vehicle is converted to another form of energy usable by the launch vehicle. The optical power is optically focused into a reaction chamber to impinge on a refractory target. A working fluid is regeneratively fed to a heat exchanger contained within the actively cooled fiber spooler. The working fluid is pre-heated within the heat exchanger and injected into the reaction chamber where the working fluid heats and expands. The exhaust is channeled through a rocket nozzle to produce thrust. In an alternative embodiment, the optical fiber expended during launch of a spacecraft is recovered.

We claim: 
     
       1. A method of launching a spacecraft into low Earth orbit using an optical power transfer system, said method comprising the steps of:
 generating high optical power at a base station; 
 transmitting said high optical power to a launch vehicle via an actively cooled fiber spooler on said launch vehicle, said transmitting step performed using an optical fiber, wherein the optical communication between said base station and said launch vehicle may be direct non-line-of-sight communication; 
 converting said high optical power received by said launch vehicle to another form of energy usable by said launch vehicle; 
 optically focusing said high optical power into a reaction chamber to impinge on a refractory target; 
 regeneratively feeding a working fluid to a heat exchanger contained within said actively cooled fiber spooler, said actively cooled fiber spooler positioned within the path of said working fluid flow; 
 regeneratively pre-heating of said working fluid within said heat exchanger, said regeneratively pre-heating step performed by extracting heat from said high optical power and from said actively cooled fiber spooler; 
 injecting said working fluid into said reaction chamber; 
 heating and expanding said working fluid within said reaction chamber; and 
 channeling the exhaust through a rocket nozzle to produce thrust. 
 
     
     
       2. The method of launching a spacecraft into low Earth orbit, as recited in  claim 1 , wherein said refractory target is a plasma core impinged by a focused beam. 
     
     
       3. The method of launching a spacecraft into low Earth orbit, as recited in  claim 1 , wherein said refractory target is a plurality of heat exchangers impinged by an expanded beam. 
     
     
       4. The method of launching a spacecraft into low Earth orbit, as recited in  claim 2 , wherein during initial flight of said launch vehicle, said working fluid for said injecting step is comprised of atmospheric air. 
     
     
       5. The method of launching a spacecraft into low Earth orbit, as recited in  claim 4 , wherein at approximately 20-30 kilometers of altitude of said launch vehicle, said working fluid for said injecting step is comprised of a mixture of atmospheric air and water or other fuel. 
     
     
       6. The method of launching a spacecraft into low Earth orbit, as recited in  claim 4 , wherein at exo-atmospheric flight of said launch vehicle, said working fluid for said injecting step is comprised solely of water. 
     
     
       7. The method of launching a spacecraft into low Earth orbit, as recited in  claim 1 , wherein said high optical power is in the range of kilowatts to tens of megawatts.